Characterization of Unsteady Interaction Phenomena of Shock Waves and Turbulent Boundary Layers in Supersonic Internal Flows

超音速内流中激波与湍流边界层非定常相互作用现象的表征

• 批准号: 14550136
• 负责人: SUGIYAMA Hiromu
• 金额: $ 2.3万
• 依托单位: Muroran Institute of Technology
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 财政年份: 2002
• 资助国家: 日本
• 起止时间: 2002 至 2003
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-14550136/
• 关键词: Pseudo Shock Waves; Shock-Boundary Layer Interaction; Supersonic Flow; Turbulent Flow; Shearing Stress; Liquid Crystal; Computational Fluid Dynamics; SCRAM Jet Engine; 剪断力; レーザードップラー流速測定(LDV); パーティクルイメージング流速測定(PIV); シュリーレン法

In order to obtain principles for optimum designs of scramjet engines, this study aims to clarify the structure and the characteristics of shock wave/boundary layer interactions in a rectangular duct imitating a separator between the intake and the combustor in scramjet engines.Firstly, the following techniques were established for a particle imaging velocimetry with high resolution and stability :1.An Impinging-type nozzle, which can inject water particles directly into the settling chamber of supersonic wind tunnels, was designed and applied to seeding of tracer particles. Water particles with sufficiently small diameter of μm were produced due to air-assisted atomizing effects and followed the air flows satisfactorily.2.Traverse equipments with high rigidity and optical equipments with high resolution were assembled. Errors in flow speed measurements were reduced to be 2.6%.In addition, the structure of turbulent boundary-layer separation on walls was investigated as follows :3.A technique for visualizing shearing stress distributions on walls using cholestric liquid crystal was established.4.High-speed changes in pressure distributions on walls were measured and analyzed using high-speed pressure transducers.5.Detailed structure of the flow field was analyzed by computational fluid dynamics.Consequently, the principle structure and the mechanism of shock wave/boundary layer interactions in a rectangular duct were clarified.

为了获得超燃冲压发动机优化设计的原则，本文以超燃冲压发动机进气道与燃烧室之间的分离器为模拟对象，研究了矩形通道内激波/边界层干扰的结构和特性。1.设计了一种可直接向超声速风洞沉降室内喷射水粒子的撞击式喷嘴，并将其应用于示踪粒子的播撒。利用气辅雾化作用，产生了足够小的粒径为μm的水粒子，并使其随气流运动。2.组装了高刚度的横向装置和高分辨率的光学装置。此外，还研究了壁面湍流边界层分离的结构：3.建立了一种基于胆甾液晶的壁面剪切应力可视化技术; 4.利用高速压力传感器测量并分析了壁面压力分布的高速变化; 5.利用计算流体力学方法分析了流场的详细结构，从而阐明了矩形通道内激波/边界层相互作用的基本结构和机理。

项目成果

L.Q.Sun, H.Sugiyama, K.Mizobata, K.Fukuda: "Numerical and Experimental Investigations on the Mach 2 Pseudo-Shock Wave in a Square Duct"Journal of Visualization. Vol.6, No.4. 363-370 (2003)

L.Q.Sun、H.Sugiyama、K.Mizobata、K.Fukuda：“方管中马赫 2 伪冲击波的数值和实验研究”可视化杂志。

H.Sugiyama, K.Fukuda, K.Mizobata, L.Sun, R.Minato: "Experimental Investigation on Shock Wave and Turbulent Boundary Layer Interactions in a Square Duct at mach 2 and 4"International Gas Turbine Congress 2003 Tokyo. (2003)

H.Sugiyama、K.Fukuda、K.Mizobata、L.Sun、R.Minato：“2 和 4 马赫方形管道中冲击波和湍流边界层相互作用的实验研究”2003 年东京国际燃气轮机大会。

Koichi FUKUDA, Hiromu SUGIYAMA, Kazuhide MIZOBATA, Liqun SUN: "Experimental Investigation on Flow Structure of Mach 4 Pseudo-Shock Wave in a Square Duct"Transactions of the Visualization Society of Japan, (in Japanese). Vol.23, No.5 May. 39-45 (2003)

Koichi FUKUDA、Hiromu SUGIYAMA、Kazuhide MIZOBATA、Liqun SUN：“方形管道中 4 马赫伪冲击波流动结构的实验研究”日本可视化协会汇刊，（日文）。

杉山弘, 福田浩一, 溝端一秀, 遠藤清和, 孫立群, 新井隆景: "衝撃波を伴う超音速内部流動に関する研究(超音速内部流動実験装置の開発およびマッハ2と4の擬似衝撃波の特性)"日本機械学会論文誌(B編). 68巻676号. 67-73 (2002)

Hiroshi Sugiyama、Koichi Fukuda、Kazuhide Mizobata、Kiyokazu Endo、Gun Tate Son、Takakage Arai：“伴随冲击波的超音速内流研究（超音速内流实验装置的开发以及2马赫和4马赫模拟冲击波的特性）”日本机械工程学会杂志（B 版）第 68 卷第 676. 67-73（2002 年）。

福田浩一, 杉山弘, 溝端一秀, 孫立群: "正方形ダクト内のマッハ4擬似衝撃波の流れ構造に関する実験的研究"可視化情報学会論文集. Vol.23, No.5. 39-45 (2003)

Koichi Fukuda、Hiroshi Sugiyama、Kazuhide Mizobata、Gun Tate Son：“方形管道中马赫数伪激波流动结构的实验研究”可视化信息学会论文集第 23 卷，第 5 期。 (2003)